Comparison of Turbulence Models for Flow Past NACA0015 Airfoil Using OpenFOAM

Abstract

Abstract. The open source code software, OpenFOAM, was applied for simulating flow past NACA0015 airfoil. Three economical turbulence models for aerospace applications were selected comprising Spalart-Allmaras model, Wilcox model and Menter SST model, respectively. The non-dimension y + was used to analyze the near-wall flow. The C-type domain for airfoil simulation was considered for an appropriate dimension to protect the effect of boundary conditions. The zero pressure gradient problem of the pressure-velocity coupling was used an effective algorithm, SIMPLE, for solving. The central differencing, upwind differencing, and linear upwind differencing (LUD) scheme were used to solve the convection-diffusion equation of the flow past airfoil. The simulation results included lift coefficient (CL) and drag coefficient (CD) were obtained from this computational fluid dynamics (CFD) method. The turbulence models had been validated to the physical experiment. The wind tunnel was set up to test the flow past NACA0015 airfoil. The Reynolds number (Re) at 160,000 and 360,000 were controlled in order that the NACA0015 airfoil with the large range angle of attack from 0 to 20 degrees was immersed in the low wind speeds and turbulent flow. The suitable turbulence model was the Menter SST model which employed SIMPLE algorithm and LUD scheme for solving. These CFD results lower the stall angle of attack had the average errors of CL and CD with were less than 13.15% and 22.36%, respectively.

Numerical and Experimental Investigation of NACA-0018 Wind Turbine Aerofoil Model Performance for Different Aspect Ratios

“…Menter SST k-ω türbülans modeli, sınır tabakada içerisinde daha hassas çözüm elde etme için Wilcox k-ω modelinin yeniden değerlendirilmesi sonucu geliştirilmiştir [10]. İki denklemli olan Menter SST k-ω modeli aşağıdaki gibi ifade edilmiştir [10,[22][23][24][25][26][27][28]:…”

“…Burada, k türbülans kinematik enerji, w türbülanslı frekans, µ dinamik viskozite, y katı duvara olan mesafe olarak tanımlanmıştır. Eşitliklerde bulunan sabitlerden olan σk, β*, σw1, γ2, β2 ve σw2 sırasıyla 1, 0,09, 2, 0,44, 0,083 ve 1,17 değerlerine sahiptir [10]. Kanat profillerinin aerodinamik performanslarının incelenmesinde kaldırma katsayısı (CL), sürükleme katsayısı (CD) ve aerodinamik verim (CL/CD) en önemli değişkenlerdir.…”

“…Ayrıca elde edilen sayısal sonuçlar FX 63-137 tipi kanat profilinin deneysel verileri ile doğrulanmıştır. Suvanjumrat [10], açık kaynak kodlu HAD analiz programı olan OpenFOAM TM kullanarak NACA-0015 kanat profili etrafındaki akışı Spalart Allmaras, Wilcox k-ω ve Menter SST k-ω modelinden oluşan üç farklı ekonomik türbülans modeli ile ayrı ayrı incelemiş ve kanat profilinin performansını ifade etmede kullanılan CL ve CD katsayılarını elde etmiştir. Çözümlenen sayısal sonuçlar NACA-0015 kanat profili için yapılan deneysel sonuçlar ile karşılaştırılmış ve yapılan karşılaştırılma neticesinde CL ve CD katsayıları sırasıyla %13,15 ve %22,36 kadarlık bir hata ile en iyi ifade eden türbülans modelinin Menter SST k-ω modeli olduğu sonucuna varılmıştır.…”

The Experimental investigation and Numerical Analysis on Horizontal Axis Wind Turbine with Winglet and Pitch Variations

“…In designing the shape of the blade, chord (c) value and twist angle (β) is needed. There are two distributions to calculate optimization of the chord length and twist angle, namely Betz and Schmitz distributions [18]. The distribution used in this study is Schmitz distribution because it has the shape of chord distribution and twists angle, it because is easy to be made and result from high solidity value.…”

Numerical Simulation Studies on Stall Suppression of a NACA0015 Airfoil

“…namely the Transition SST, k-S SST, realizable k-T and S-A model based on same cell structure domain. In Figures2(f), 2(g) and 2(h), computed lift coefficients (CL), drag coefficients (CD) and sliding ratio (CL/CD) values varying angles of attack (AOA, Q) from 0° to 20° with an interval of 2°at Reynolds number of 1.6×10 5 are compared with the experimental data of Suvanjumrat, 2016[9].…”